CN115042980A - Solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle - Google Patents
Solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle Download PDFInfo
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- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 72
- 238000004146 energy storage Methods 0.000 title claims abstract description 72
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 72
- 239000001257 hydrogen Substances 0.000 title claims abstract description 72
- 239000000446 fuel Substances 0.000 claims abstract description 44
- 238000010248 power generation Methods 0.000 claims abstract description 12
- 238000002910 structure generation Methods 0.000 claims abstract description 5
- 210000004027 cell Anatomy 0.000 claims description 54
- 238000000034 method Methods 0.000 claims description 13
- 210000000352 storage cell Anatomy 0.000 claims description 12
- 239000003381 stabilizer Substances 0.000 claims description 10
- 230000009194 climbing Effects 0.000 claims description 9
- 230000008569 process Effects 0.000 claims description 9
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 6
- 229910052744 lithium Inorganic materials 0.000 claims description 6
- 230000003068 static effect Effects 0.000 claims description 6
- 230000017525 heat dissipation Effects 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 230000001133 acceleration Effects 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 238000002474 experimental method Methods 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 238000005381 potential energy Methods 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 238000004088 simulation Methods 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims description 2
- 238000005265 energy consumption Methods 0.000 claims description 2
- 238000012544 monitoring process Methods 0.000 claims description 2
- 230000002035 prolonged effect Effects 0.000 claims description 2
- 230000000087 stabilizing effect Effects 0.000 claims 2
- 210000003850 cellular structure Anatomy 0.000 abstract description 4
- 230000000149 penetrating effect Effects 0.000 abstract 1
- 230000001914 calming effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
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- B64D27/026—
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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- B64D27/353—
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Abstract
The invention discloses a solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle, and belongs to the field of aeronautical engineering. The invention comprises a distributed solar wing, a nacelle body, a power system and a tail wing. The invention utilizes the advantages of three energy sources, namely solar battery infinite power generation in daytime, high specific energy of hydrogen fuel battery and high specific power of energy storage battery, fully exerts the advantages of multiple energy sources and realizes the advantages of green and long-endurance flight of the electric unmanned aerial vehicle. The invention adopts a distributed layout of a wing middle section and two wing outer sections, structural solar cell components are respectively paved on the upper surfaces of the wing middle section and the wing outer sections, and the solar cell components have double functions of skin structure and power generation; an open-cell nacelle body having an air flow passage; the integral penetrating type layout from the empennage, the wings to the power system is adopted; the empennage and the power system share the connecting pipe, and the box-shaped structure is formed by the empennage, the connecting rod and the wings, so that the structural quality can be reduced, and the structural strength is improved.
Description
Technical Field
The invention relates to a solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle, and belongs to the field of aeronautical engineering.
Background
At present, the environmental problems at home and abroad are increasingly serious, the problem of fossil energy supply is increasingly tense, various countries strive to promote renewable energy sources to replace traditional fossil fuels, and clean and pollution-free new energy sources become main energy sources in the fields of aircrafts and the like in the future. An aircraft driven by green energy such as a solar cell and a hydrogen fuel cell has become one of the research hotspots in various countries.
Solar energy unmanned aerial vehicle maintains the unmanned aerial vehicle flight through the solar cell of wing upper surface at the electricity generation on daytime, and the residual energy charges for energy storage battery, utilizes modes such as energy storage battery to supply energy for unmanned aerial vehicle night. The solar energy is continuous in source and can fly permanently in theory. However, limited by the current conversion efficiency of the solar cell and the energy density of the energy storage cell, the solar unmanned aerial vehicle needs to adopt a series of technologies (such as adopting a high aspect ratio and a low wing load technology to reduce flight power consumption and reduce payload carrying so as to increase energy supply) to realize permanent flight, so that the unmanned aerial vehicle has a relatively soft structure, poor maneuverability, low payload and a simple application scene.
Hydrogen fuel cell unmanned aerial vehicle passes through hydrogen fuel cell and turns into the electric energy with hydrogen energy to realize unmanned aerial vehicle's long voyage flight. Compared with a solar unmanned aerial vehicle, the unmanned aerial vehicle is hardly influenced by weather changes; compare in lithium cell unmanned aerial vehicle, its hydrogen energy density is high, and considerable energy can be supplied to the hydrogen of small mass. However, due to the limitation of the specific power of the hydrogen fuel cell and the influence of fuel diffusion and battery chemical reaction, the dynamic response of the unmanned aerial vehicle energy supply is slow, and the electric characteristics are soft. The fuel cell driven aircraft is adopted only, so that the maneuvering performance of the unmanned aerial vehicle is difficult to guarantee, and the task requirement is met at a high cost.
Disclosure of Invention
The invention aims to provide a solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle, which utilizes the respective advantages of three energy sources, namely infinite power generation by a solar battery in the daytime, high specific energy of a hydrogen fuel battery and high specific power of an energy storage battery, fully exerts the advantages of various energy sources and realizes the advantages of green and long-endurance flight of the electric unmanned aerial vehicle.
The purpose of the invention is realized by the following technical scheme
The invention discloses a solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle which comprises distributed solar wings, a nacelle body, a power system and a tail wing.
The distributed solar wing adopts a conventional layout with a large display ratio, mainly comprises a middle section solar wing and two outer sections solar wings, namely structural distributed solar components are respectively paved on the upper surfaces of the middle section solar wing and the outer sections solar wing, and the structural distributed solar components are embedded into a wing structure and have dual functions of a skin structure and power generation. The distributed solar wing not only can bring higher lift-drag ratio and save structural quality, but also can bring continuous energy for the hybrid unmanned aerial vehicle in the daytime, and avoids the problem of power mismatch in the solar battery assembly.
And the power system is used for outputting power and providing tension for the fixed-wing unmanned aerial vehicle. The power system is a front-mounted double-power generator, is positioned on two sides of a symmetry axis of the front edge of the distributed solar wing, and mainly comprises a propeller, an electric driver and a fixing piece. The mounting is fixed on the connecting pipe, the mounting is fixed in on the unmanned aerial vehicle, the root of screw with the electric drive carries out fastening connection, the electric drive with the bus connection of three kinds of energy, drives when accepting one or more energy supply the screw rotates and produces the pulling force together, realizes the whole section of unmanned aerial vehicle, flies during the long voyage of full envelope.
The nacelle body is positioned on the symmetry axis of the distributed solar wing, the energy storage battery, the hydrogen fuel cell system and the airborne equipment are loaded in the inner space of the nacelle body, the front side surface of the nacelle body is provided with an air inlet hole, the rear side surface of the nacelle body is provided with an air outlet hole, and the hydrogen fuel cell system is placed in an air flow channel close to the air outlet hole according to simulation and experiments to realize the heat dissipation and the heat management of the hydrogen fuel cell system; the energy storage battery is used for longitudinal balancing of the machine body. When cruising and flying at night for long voyage, the hydrogen fuel cell system with high specific energy is adopted to supply power; when the long-endurance task flies in the daytime, the solar battery on the distributed solar wing is adopted for supplying power, and the rest energy is stored in the energy storage battery; the energy storage battery is used for supplying power to high current and power in day and night flight. The hydrogen fuel cell system with high specific energy, the energy storage battery with high specific energy and the solar battery with infinite power generation supply fully utilize respective advantages, and green and long-endurance flight of the electric unmanned aerial vehicle is realized.
The empennage adopts two parts of a horizontal empennage and a double vertical empennage for controlling and balancing the three-dimensional plane flight of the unmanned aerial vehicle, and the stable flight of the unmanned aerial vehicle in a middle and low altitude complex environment is realized. Horizontal fin includes horizontal stabilizer and elevator, horizontal stabilizer guarantees unmanned aerial vehicle's level stability, the elevator is used for unmanned aerial vehicle's longitudinal operation. The two perpendicular fin include two perpendicular planes of calming and two rudders, perpendicular planes of calming guarantee that unmanned aerial vehicle's transverse motion is stable, the rudder is used for unmanned aerial vehicle's transverse motion to the operation, and two perpendicular fin overall arrangement reduce unmanned aerial vehicle's whole focus, increase transverse motion stability and maneuverability. In addition, the fin runs through distributed solar energy wing chord to with driving system uses the connecting pipe jointly, lightens structure weight, horizontal fin, two perpendicular fins, connecting pipe and distributed solar energy wing have wholly constituted box-type structure, reinforcing unmanned aerial vehicle bulk strength.
In order to realize the running takeoff on the runway of the unmanned aerial vehicle, the unmanned aerial vehicle preferably comprises an undercarriage, the undercarriage is a three-point nose undercarriage, the three-point nose undercarriage comprises a main undercarriage and a nose undercarriage, the main undercarriage is shaped like a Chinese character 'ji', the nose undercarriage is arranged behind the gravity center of the airframe, the nose undercarriage is a strut-shaped undercarriage, the structural weight is reduced, and the stability of the running process of the takeoff and landing of the unmanned aerial vehicle is improved.
In order to improve the lift-drag aerodynamic efficiency of the solar/hydrogen/energy storage battery hybrid power unmanned aerial vehicle, the aspect ratio of the distributed solar wing is 12-18.5 as the optimal selection. For better real-time monitoring and tracking of parameters of the distributed solar modules, it is preferable that each module of the distributed solar wing is equipped with a single or multiple Maximum Power Point Trackers (MPPTs) to achieve maximum power output of the system while changing the power mismatch problem of the solar module.
In order to guarantee the high power discharge of whole section of unmanned aerial vehicle, full envelope, as preferred, energy storage battery chooses for use high energy, high magnification, long-life lithium cell.
In order to fully and effectively utilize the tri-electric hybrid energy under the condition of limited input energy, the hybrid power system preferably adopts an energy manager to perform hybrid energy management on a distributed solar battery, an MPPT (maximum power point tracking), an energy storage battery, a hydrogen fuel cell system and a power system, and the energy manager adopts an active or passive energy management strategy, so that the energy consumption of the unmanned aerial vehicle flying at each task section is minimum, and the flying time of the tri-electric hybrid power unmanned aerial vehicle is prolonged.
In order to reduce the structural mass and cost, the connecting pipes of the unmanned aerial vehicle, namely the connecting pipes of the tail wing, the distributed solar wings and the power system are preferably connected by adopting an integrated carbon fiber pipe.
As an alternative, the drone includes a pair of ailerons disposed at the trailing edge outboard of the wing for controlling the rolling operation of the drone.
The invention discloses a working method of a solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle, which comprises the following steps:
in the takeoff phase, the unmanned aerial vehicle takes off from a static acceleration to a ground-off speed on a runway and climbs to a safe height in the air. In the stage, the energy storage battery supplies power to the power system, namely the energy storage battery supplies power to the electric driver to drive the propeller to rotate, so that the tension for driving the undercarriage to slide is generated when the undercarriage slides on the ground, and the tension for overcoming air resistance is generated when the undercarriage slides in the air.
In the climbing stage, the unmanned aerial vehicle starts from the safe takeoff height and reaches the cruising height according to a certain climbing speed and a certain climbing angle. In the stage, three kinds of energy sources including a solar cell, a hydrogen fuel cell and an energy storage cell are supplied in a mixed mode, the solar cell is preferentially used for supplying energy, the hydrogen fuel cell system is mainly used for supplying power, and the energy storage cell is used for supplying power for assisting in supplying energy.
And under the task cruising and the hovering, the unmanned aerial vehicle performs long-endurance task flight according to the task requirement and the target of the maximum endurance or the maximum range. In the stage, the solar battery is mainly used in the daytime, and the energy storage battery is charged by the residual energy; the hydrogen fuel cell system is mainly used for supplying power at night, and the energy storage battery is used for assisting.
In the descending stage, the unmanned aerial vehicle descends from the task height to enter the descending task stage, potential energy is converted into kinetic energy required by the unmanned aerial vehicle, the output power of the power system in the process is low, and the power system is mainly powered by the hydrogen fuel cell system.
Under the landing stage, unmanned aerial vehicle descends to behind the buffer height, relies on aerodynamic force to decelerate, and unmanned aerial vehicle lands ground when speed descends to a certain degree, relies on aerodynamic force and ground frictional resistance to decelerate until the aircraft is static. The process is powered by a hybrid of the remaining hydrogen fuel cell system and the lithium battery.
Has the advantages that:
1. the solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle disclosed by the invention comprehensively exerts three energy advantages of infinite power generation of the solar battery in the daytime, high specific energy of the hydrogen fuel battery and high specific power of the energy storage battery, and realizes the flight advantages of green and long voyage of the electric unmanned aerial vehicle.
2. The invention discloses a solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle, which adopts a distributed layout of a solar wing middle section and two solar wing outer sections, wherein the upper surfaces of the distributed wings respectively adopt solar cell components embedded into wing structures, and the solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle has the double functions of skin structure and power generation, thereby not only saving the structural weight and improving the lift-drag ratio of the aircraft, but also avoiding the problem of power mismatch caused by uneven irradiation of the solar cell components.
3. The invention discloses a solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle, which is provided with a perforated nacelle body with an air flow channel, wherein the front side surface of the nacelle body is provided with air inlet holes respectively, the rear side surface of the nacelle body is provided with air outlet holes, and a hydrogen fuel battery system is placed in the air flow channel between the air inlet holes and the air outlet holes, so that the heat dissipation and the heat management of the hydrogen fuel battery system in the nacelle body are realized.
4. The invention discloses a solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle, which adopts a through type airframe layout method, namely, the integral through type layout from an empennage, a distributed solar energy airframe to a power system is adopted, the empennage and the power system share a connecting pipe, and a box type structure is formed by the empennage, the connecting rod and the distributed solar energy airframe, so that the structural quality can be reduced, and the structural strength is increased.
Drawings
Fig. 1 is a side view of a solar/hydrogen/energy storage battery hybrid drone according to an embodiment of the present invention;
fig. 2 is a top view of a hybrid solar/hydrogen/energy storage battery drone according to one embodiment of the present disclosure;
fig. 3 is a front view of a hybrid solar/hydrogen/energy storage battery drone according to one embodiment of the invention;
fig. 4 is a left side view of a solar/hydrogen/energy storage battery hybrid drone according to one embodiment of the present disclosure;
wherein: 1. a distributed solar wing; 2. a power system; 3. a nacelle fuselage; 4. a tail wing; 5. an aileron; 6. a connecting pipe; 7. an air hole; 8. a hydrogen fuel cell system; 9. an energy storage battery; 10. a main landing gear; 11. a nose landing gear; 1.1, middle wing; 1.2, outer section wing; 1.3, a solar cell module with a middle-section structure; 1.4, an outer segment structure solar cell module; 2.1, an electric driver; 2.2, a propeller; 4.1 horizontal stabilizer; 4.2 elevators; 4.3 vertical stabilizer; 4.4 rudder; 7.1, air inlet holes; 7.2 and air outlet holes.
Detailed Description
To better illustrate the objects and advantages of the present invention, the following description is provided in conjunction with the examples.
Example 1:
fig. 1 to 4 are a side view, a top view, a front view and a left side view of the unmanned aerial vehicle, respectively. With reference to fig. 1-4, the example drone includes a distributed solar wing 1, a nacelle fuselage 2, a power system 3, and a tail 4.
The distributed solar wing 1 adopts a conventional layout with a large aspect ratio and mainly comprises a middle section wing 1.1, an outer section wing 1.2, a middle section structure solar battery component 1.3 and an outer section structure solar battery component 1.4. The upper surfaces of the middle section wing 1.1 and the outer section wing 1.2 are respectively paved with a middle section structure solar battery component 1.3 and an outer section structure solar battery component 1.4, namely the distributed solar battery components are embedded into the structure of the distributed wing, and the double functions of skin structure and power generation are achieved. Each distributed component of the distributed solar wing 1 is equipped with a single or multiple Maximum Power Point Trackers (MPPT) to achieve the maximum power output of the system. The distributed solar wing not only can bring higher lift-drag ratio and save structural mass, but also can bring continuous energy for the hybrid power unmanned aerial vehicle in the daytime, and avoids the problem of power mismatch in the solar battery component.
The nacelle body 3 is positioned on the symmetry axis of the distributed solar wing, the hydrogen fuel cell system 8, the energy storage cell 9 and the airborne equipment are loaded in the inner space of the nacelle body, the front side surface of the nacelle body is provided with an air inlet hole 7.1, the rear side surface of the nacelle body is provided with an air outlet hole 7.2, and the hydrogen fuel cell system 8 is placed in an air flow channel close to the air outlet hole according to simulation and experiments to realize heat dissipation and heat management of the hydrogen fuel cell system; the energy storage battery 9 is a lithium battery with high energy, high multiplying power and long service life, and is used for longitudinal balancing of a machine body. When cruising and flying at night in long voyage, a hydrogen fuel cell system with high specific energy is adopted to supply power; in the daytime, when the long-endurance mission flies, the solar battery with infinite power generation is adopted for power supply, and the rest energy is stored in the energy storage battery; the energy storage battery is used for supplying power to high current and power in daytime and night flight. The advantages of the hydrogen fuel cell with high specific energy, the energy storage cell with high specific energy and the solar cell for unlimited power generation are fully utilized, and green and long-endurance flight of the electric unmanned aerial vehicle is realized.
The empennage 4 consists of a horizontal stabilizer 4.1, an elevator 4.2, a vertical stabilizer 4.3 and a rudder 4.4, and is used for controlling and balancing the three-dimensional plane flight of the unmanned aerial vehicle, so that the unmanned aerial vehicle can stably fly in a medium and low altitude complex environment. Horizontal stabilizer 4.1 guarantees unmanned aerial vehicle's horizontal stability, elevator 4.2 is used for unmanned aerial vehicle's longitudinal operation, perpendicular stabilizer 4.3 adopts two vertical fin forms to guarantee unmanned aerial vehicle's transverse direction stable, rudder 4.4 adopts two rudder surface forms for unmanned aerial vehicle's transverse direction operation, two perpendicular fin overall arrangement reduce unmanned aerial vehicle's whole focus, have increased transverse direction stability and maneuverability. In addition, the fin run through distributed solar energy wing chord to with driving system uses the connecting pipe jointly, connecting pipe formula carbon fiber pipe as an organic whole alleviates structural weight, fin 4, connecting pipe 6 and distributed solar energy wing 1 have wholly constituted box-shaped structure, reinforcing unmanned aerial vehicle bulk strength.
The undercarriage adopts the three point type undercarriage in front, including main undercarriage 10 and nose undercarriage 11, main undercarriage 10 adopts the style of calligraphy, sets up behind the organism focus, nose undercarriage 11 adopts the pillar shape undercarriage, alleviates structural weight, increases the stability of unmanned aerial vehicle take-off and landing running process.
In this embodiment, the drone comprises a pair of ailerons 5, which are disposed at the trailing edge outside the distributed solar wings, for controlling the roll operation of the drone.
The working method of the solar energy/hydrogen energy/energy storage battery hybrid power unmanned aerial vehicle disclosed by the embodiment comprises the following steps:
in the takeoff phase, the unmanned aerial vehicle takes off from a static acceleration to a ground-off speed on a runway and climbs to a safe height in the air. In the stage, the power system 2 is powered by the energy storage battery 9, namely the energy storage battery supplies power to the electric driver 2.1 to drive the propeller 2.2 to rotate, so that the pulling force for driving the main undercarriage 8 and the nose undercarriage 9 to run is generated during ground running, and the pulling force for overcoming air resistance is generated during air running.
In the climbing stage, the unmanned aerial vehicle starts from the safe takeoff height and reaches the cruising height according to a certain climbing speed and a certain climbing angle. In the stage, three kinds of energy sources, namely the distributed solar wing 1, the hydrogen fuel cell system 8 and the energy storage cell 9, are supplied in a mixed manner, the solar cell in the distributed solar wing 1 is preferentially used for supplying energy, the hydrogen fuel cell system 8 is mainly used for supplying power, and the energy storage cell 9 is used for supplying power as an auxiliary energy source.
And under the task cruising and the hovering, the unmanned aerial vehicle performs long-endurance task flight according to the task requirement and the target of the maximum endurance or the maximum range. In this stage, the solar battery in the distributed solar wing 1 is mainly used in the daytime, and the residual energy charges the energy storage battery 9; the power supply of the hydrogen fuel cell system 8 is taken as the main part at night, and the energy storage cell 9 is taken as the auxiliary part.
In the descending stage, the unmanned aerial vehicle descends from the task height to enter the descending task stage, potential energy is converted into kinetic energy required by the unmanned aerial vehicle, the output power of the power system in the process is low, and the power system is mainly powered by the hydrogen fuel cell system 8.
Under the landing stage, unmanned aerial vehicle descends to behind the buffer height, relies on aerodynamic force to decelerate, and unmanned aerial vehicle lands ground when speed descends to a certain degree, relies on aerodynamic force and ground frictional resistance to decelerate until the aircraft is static. The process is powered by the remaining hydrogen fuel cell system 8 and the energy storage battery 9 in a hybrid manner.
The above detailed description is further intended to illustrate the objects, technical solutions and advantages of the present invention, and it should be understood that the above description is only an example of the embodiments of the present invention, and is only used for explaining the present invention, and is not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. The utility model provides a solar energy/hydrogen energy/energy storage battery hybrid unmanned aerial vehicle which characterized in that: the system comprises a distributed solar wing, a nacelle body, a power system and a tail wing;
the distributed solar wing adopts a conventional layout with a large aspect ratio and mainly comprises a middle section solar wing and two outer sections solar wings, namely, structural distributed solar components are respectively paved on the upper surfaces of the middle section solar wing and the outer sections solar wing, and are embedded into a wing structure, so that the distributed solar wing has the dual functions of a skin structure and power generation. The distributed solar wing not only can bring higher lift-drag ratio and save structural mass, but also can bring continuous energy for the hybrid unmanned aerial vehicle in the daytime, and avoids the problem of power mismatch in the solar cell module;
the power system is used for outputting power and providing tension for the fixed-wing unmanned aerial vehicle; the power system is a front-mounted double-power generator, is positioned on two sides of a symmetrical axis of the front edge of the distributed solar wing and mainly comprises a propeller, an electric driver and a fixing piece; the fixing piece is fixed on the connecting pipe, the fixing piece is fixed on the unmanned aerial vehicle, the root of the propeller is fixedly connected with the electric driver, the electric driver is connected with the bus of the three energy sources, and the propeller is driven to rotate together to generate tension when receiving one or more energy sources, so that the long-endurance flight of the whole section and the full-envelope line of the unmanned aerial vehicle is realized;
the nacelle body is positioned on the symmetry axis of the distributed solar wing, the energy storage battery, the hydrogen fuel cell system and the airborne equipment are loaded in the inner space of the nacelle body, the front side surface of the nacelle body is provided with an air inlet hole, the rear side surface of the nacelle body is provided with an air outlet hole, and the hydrogen fuel cell system is placed in an air flow channel close to the air outlet hole according to simulation and experiments to realize the heat dissipation and heat management of the hydrogen fuel cell system; the energy storage battery is used for longitudinal balancing of the machine body. When cruising and flying at night for long voyage, the hydrogen fuel cell system with high specific energy is adopted to supply power; when the long-endurance task flies in the daytime, the solar battery on the distributed solar wing is adopted for supplying power, and the rest energy is stored in the energy storage battery; the energy storage battery is used for supplying power to high current and power in day and night flight. The hydrogen fuel cell system with high specific energy, the energy storage cell with high specific energy and the solar cell with infinite power generation supply three energy sources fully utilize respective advantages to realize green and long-endurance flight of the electric unmanned aerial vehicle;
the tail wing adopts two parts, namely a horizontal tail wing and a double vertical tail wing, and is used for controlling and balancing the three-dimensional plane flight of the unmanned aerial vehicle so as to realize the stable flight of the unmanned aerial vehicle in a medium and low altitude complex environment; the horizontal tail wing comprises a horizontal stabilizer and an elevator, the horizontal stabilizer ensures the horizontal stability of the unmanned aerial vehicle, and the elevator is used for the longitudinal operation of the unmanned aerial vehicle; the double vertical tail wings comprise two vertical stabilizing surfaces and two rudders, the vertical stabilizing surfaces ensure the stability of the transverse direction of the unmanned aerial vehicle, the rudders are used for the transverse operation of the unmanned aerial vehicle, the overall gravity center of the unmanned aerial vehicle is reduced due to the arrangement of the double vertical tail wings, and the stability and the maneuverability of the transverse direction are improved; in addition, the fin runs through distributed solar energy wing chord to with driving system uses the connecting pipe jointly, lightens structure weight, horizontal fin, two perpendicular fins, connecting pipe and distributed solar energy wing have wholly constituted box-type structure, reinforcing unmanned aerial vehicle bulk strength.
2. The solar/hydrogen/energy storage battery hybrid unmanned aerial vehicle of claim 1, wherein: in order to realize the running takeoff on the runway of the unmanned aerial vehicle, the unmanned aerial vehicle comprises an undercarriage, the undercarriage is a front three-point undercarriage, the front three-point undercarriage comprises a main undercarriage and a front undercarriage, the main undercarriage is shaped like a Chinese character 'ji', the main undercarriage is arranged behind the gravity center of the airframe, the front undercarriage is a strut-shaped undercarriage, the structural weight is reduced, and the stability of the takeoff and landing running process of the unmanned aerial vehicle is improved.
3. The solar/hydrogen/energy storage battery hybrid unmanned aerial vehicle of claim 1, wherein: in order to improve the lift-drag aerodynamic efficiency of the solar/hydrogen/energy storage battery hybrid power unmanned aerial vehicle, the aspect ratio of the distributed solar wing is 12-18.5; for better real-time monitoring and tracking of parameters of distributed solar modules, each module of the distributed solar wing is equipped with a single or multiple maximum power point trackers MPPT to achieve maximum power output of the system while changing the power mismatch problem of the solar modules.
4. The solar/hydrogen/energy storage battery hybrid unmanned aerial vehicle of claim 1, wherein: in order to guarantee the high power discharge of whole section of unmanned aerial vehicle, full envelope, energy storage battery chooses for use high energy, high magnification, long-life lithium cell.
5. The solar/hydrogen/energy storage battery hybrid unmanned aerial vehicle of claim 1 or 2, wherein: in order to fully and effectively utilize the three-electric hybrid energy under the condition of limited input energy, the hybrid power system adopts an energy manager to carry out hybrid energy management on a distributed solar battery, an MPPT (maximum power point tracking), an energy storage battery, a hydrogen fuel cell system and a power system, the energy manager adopts an active or passive energy management strategy, the energy consumption of the unmanned aerial vehicle flying at each task section is minimum, and the flying time of the three-electric hybrid power unmanned aerial vehicle is prolonged.
6. The solar/hydrogen/energy storage battery hybrid unmanned aerial vehicle of claim 1, wherein: in order to reduce the structural mass and cost, the connecting pipe of the unmanned aerial vehicle, namely the connecting pipe of the tail wing, the distributed solar wing and the power system, is connected by adopting an integrated carbon fiber pipe.
7. The solar/hydrogen/energy storage battery hybrid unmanned aerial vehicle of claim 1, wherein: the unmanned aerial vehicle includes a pair of ailerons, the aileron set up in the trailing edge in the distributed solar energy wing outside for control unmanned aerial vehicle's roll operation.
8. The solar/hydrogen/energy storage battery hybrid unmanned aerial vehicle of claim 1, 2, 3, 4, 5, 6 or 7, wherein: the working method is that,
in the takeoff phase, the unmanned aerial vehicle takes off from static acceleration to ground-off speed on a runway and climbs to a safe height in the air; at this stage, the power system is powered by the energy storage battery, namely the energy storage battery supplies power to the electric driver to drive the propeller to rotate, so that the pulling force for driving the undercarriage to run is generated when the undercarriage runs on the ground, and the pulling force for overcoming air resistance is generated when the undercarriage runs in the air;
in the climbing stage, the unmanned aerial vehicle starts from the safe takeoff height and reaches the task cruising height according to a certain climbing speed and a certain climbing angle; in the stage, three kinds of energy sources, namely a solar cell, a hydrogen fuel cell and an energy storage cell, are supplied in a mixed manner, the solar cell is preferentially used for supplying energy, the hydrogen fuel cell system is mainly used for supplying power, and the energy storage cell is used for supplying energy in an auxiliary manner;
under the condition of task cruising and hovering, the unmanned aerial vehicle flies in a long-endurance task at the maximum endurance or the maximum range according to the task requirement; in the stage, the solar battery is mainly used in the daytime, and the energy storage battery is charged by the residual energy; at night, the hydrogen fuel cell system is mainly used for supplying power, and the energy storage cell is used as an auxiliary power;
in the descending stage, the unmanned aerial vehicle descends from the task height to enter the descending task stage, potential energy is converted into kinetic energy required by the unmanned aerial vehicle, the output power of a power system is low in the process, and the power system is mainly powered by a hydrogen fuel cell system;
in the landing stage, the unmanned aerial vehicle decelerates by virtue of aerodynamic force after descending to a buffer height, and when the speed is reduced to a certain degree, the unmanned aerial vehicle lands on the ground and decelerates by virtue of aerodynamic force and ground friction resistance until the aircraft is static; the process is powered by a hybrid of the remaining hydrogen fuel cell system and the lithium battery.
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